Tracking Control of Spacecraft Attitude on Time Dependent Trajectories

摘要

A spacecraft attitude control which uses the quaternion parametrization, is proposed. The derivative of the to-go quaternion is obtained where the desired attitude is a time dependent function. Using this new attitude formulation, a Lyapunov function based feedback control law that takes the time derivative of the desired attitude into account is proposed. The simulation results demonstrate the success of the new algorithm in tracking the desired attitude trajectory.